Aircraft having VTOL, translational and traverse flight

Abstract

An aircraft capable of Vertical Take-Off and Landing (VTOL) and traverse flight. The aircraft generally includes a fixed outer structure including at least a generally cylindrical wing having an internal body situated within the fixed outer structure. A space is defined between the internal body and the fixed outer structure. Within this space are one or more rotatable ring impellers that create(s) thrust sufficient to achieve lift for the aircraft.

What is claimed is: 
     
       1. A powered-lift aircraft capable of vertical take-off and vertical landing, hovering and translational and traverse flight, comprising:
 a generally cylindrical wing having a cylindrical cavity and an inner surface, the cylindrical wing defining a central open space area; 
 one or more propulsion impeller rings rotatably supported within the cylindrical cavity of the generally cylindrical wing; 
 a cockpit or payload enclosure disposed within a portion of the central open space area and pivotally mounted to and surrounded by the generally cylindrical wing; and 
 an attitude control system configured to maintain a longitudinal axis for the cockpit or payload enclosure in a generally constant level attitude relative to earth's surface and independent of an attitude of the generally cylindrical wing; 
 wherein during vertical takeoff of the aircraft the one or more propulsion impeller rings rotate at rotational speeds that are sufficient to provide enough thrust force to overcome a weight amount of the aircraft; 
 wherein the cylindrical wing is axially horizontally oriented during level flight of the aircraft. 
 
     
     
       2. The powered-lift aircraft of  claim 1  wherein portions of the generally cylindrical wing having a non-constant cross-sectional shape contoured for providing lift. 
     
     
       3. The powered-lift aircraft of  claim 2  wherein the one or more propulsion impeller rings are a pair of propulsion impeller rings housed within the cylindrical cavity and such that a first of the pair of propulsion impeller rings rotates in a clockwise or counter-clockwise manner and the second of the pair of propulsion impeller rings rotates in an opposite manner as the rotation of the first propulsion impeller ring. 
     
     
       4. The powered-lift aircraft of  claim 1  further comprising an impeller ring drive system that is supported within the generally cylindrical wing or the cockpit or payload enclosure. 
     
     
       5. The powered-lift aircraft of  claim 1  further comprising a plurality of impeller blades that are pivotally or rotatably connected to at least one of the one or more propulsion impeller rings for variable pitch control, the plurality of impeller blades extending inward from the pivot connection to the impeller rings such that an outer portion of the plurality of impeller blades are positioned within the central open space area defined by the generally cylindrical wings and generally pointing toward the cockpit or payload enclosure. 
     
     
       6. The powered-lift aircraft of  claim 5  further comprising an asymmetric impeller blade pitch control system operatively connected to the impeller blades to allow for individual and differential control of the impeller blades by the blade pitch control system to cause the one or more propulsion impeller rings to provide asymmetrical thrust. 
     
     
       7. The powered-lift aircraft of  claim 5  wherein the impeller blades extend radially inward from at least one of the one or more of the impeller rings. 
     
     
       8. The powered-lift aircraft of  claim 5  further comprising a drive system housed within the generally cylindrical wing for individually and incrementally pivoting the plurality of impeller blades to provide variable pitch control. 
     
     
       9. The power-lift aircraft of  claim 5  wherein the plurality of impeller blades all do not pivot or rotate in a same direction at a same time and can be individually manipulated to pivot or rotate in a particular direction. 
     
     
       10. The powered-lift aircraft of  claim 1  further comprising an emergency ballistic recovery system associated with the cockpit or payload enclosure. 
     
     
       11. The powered-lift aircraft of  claim 1  wherein the cylindrical wing is axially vertically oriented during vertical flight, hovering and vertical landing of the aircraft. 
     
     
       12. The powered-lift aircraft of  claim 1  further comprising an axle extending from a first area of the cylindrical wing to a second area of the generally cylindrical wing and across the central open space area and connected to the cockpit or payload enclosure for providing pivotal communication between the cockpit or payload enclosure and the generally cylindrical wing. 
     
     
       13. The powered-lift aircraft of  claim 1  further comprising one or more powerplants secured to the generally cylindrical wing and operatively associated with the one or more propulsion impeller rings for causing the one or more propulsion impeller rings to rotate. 
     
     
       14. The power-lift aircraft of  claim 1  further comprising one or more air bearings for supporting the one or more propulsion impeller rings within the cavity of the generally cylindrical wing. 
     
     
       15. The power-lift aircraft of  claim 1  wherein the cockpit or payload enclosure having a teardrop or airfoil configuration which serves as a middle wing of a tri-fold configuration during generally level flight of the aircraft. 
     
     
       16. A powered-lift aircraft capable of vertical take-off and vertical landing, hovering and translational and traverse flight, comprising:
 a generally cylindrical wing having a cylindrical cavity and an inner surface, the cylindrical wing defining a central open space area; 
 one or more propulsion impeller rings rotatably supported within the cylindrical cavity of the generally cylindrical wing; 
 a cockpit or payload enclosure disposed within a portion of the central open space area and pivotally mounted to and surrounded by the generally cylindrical wing; 
 an impeller ring drive system that is supported within the generally cylindrical wing or the cockpit or payload enclosure; 
 a plurality of impeller blades that are pivotally or rotatably connected to at least one of the one or more propulsion impeller rings for variable pitch control, the plurality of impeller blades extending radially inward from the pivot connection to the impeller rings such that an outer portion of the plurality of impeller blades are positioned within the central open space area defined by the generally cylindrical wings and generally pointing toward the cockpit or payload enclosure; 
 an asymmetric impeller blade pitch control system operatively connected to the impeller blades to allow for individual and differential control of the impeller blades by the blade pitch control system to cause the one or more propulsion impeller rings to provide asymmetrical thrust; and 
 an attitude control system configured to maintain a longitudinal axis for the cockpit or payload enclosure in a generally constant level attitude relative to earth's surface and independent of an attitude of the generally cylindrical wing; 
 wherein during vertical takeoff of the aircraft the one or more propulsion impeller rings rotate at rotational speeds that are sufficient to provide enough thrust force to overcome a weight amount of the aircraft; 
 wherein the cylindrical wing is axially vertically oriented during vertical flight, hovering and vertical landing of the aircraft; 
 wherein the cylindrical wing is axially horizontally oriented during level flight of the aircraft. 
 
     
     
       17. The powered-lift aircraft of  claim 16  wherein portions of the generally cylindrical wing having a non-constant cross-sectional shape contoured for providing lift. 
     
     
       18. The powered-lift aircraft of  claim 16  wherein the one or more propulsion impeller rings are a pair of propulsion impeller rings housed within the cylindrical cavity and such that a first of the pair of propulsion impeller rings rotates in a clockwise or counter-clockwise manner and the second of the pair of propulsion impeller rings rotates in an opposite manner as the rotation of the first propulsion impeller ring. 
     
     
       19. The powered-lift aircraft of  claim 16  further comprising an emergency ballistic recovery system associated with the cockpit or payload enclosure. 
     
     
       20. The powered-lift aircraft of  claim 16  further comprising an axle extending from a first area of the cylindrical wing to a second area of the generally cylindrical wing and across the central open space area and connected to the cockpit or payload enclosure for providing pivotal communication between the cockpit or payload enclosure and the generally cylindrical wing. 
     
     
       21. The powered-lift aircraft of  claim 16  further comprising one or more powerplants secured to the generally cylindrical wing and operatively associated with the one or more propulsion impeller rings for causing the one or more propulsion impeller rings to rotate. 
     
     
       22. The power-lift aircraft of  claim 16  further comprising one or more air bearings for supporting the one or more propulsion impeller rings within the cavity of the generally cylindrical wing. 
     
     
       23. The power-lift aircraft of  claim 16  wherein the cockpit or payload enclosure having a teardrop or airfoil configuration which serves as a middle wing of a tri-fold configuration during generally level flight of the aircraft.